Pre-diffuser for a gas turbine engine

ABSTRACT

A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No.16/376,448 filed Apr. 5, 2019.

BACKGROUND

The present disclosure relates to a gas turbine engine and, moreparticularly, to a pre-diffuser therefor.

Gas turbine engines include a compressor section to pressurize a supplyof air, a combustor section to burn a hydrocarbon fuel in the presenceof the pressurized air, and a turbine section to extract energy from theresultant combustion gases. The compressor section discharges air into apre-diffuser upstream of the combustion section. The pre-diffuserconverts a portion of dynamic pressure to static pressure. A diffuserreceives the air from the pre-diffuser and supplies the compressed coreflow around an aerodynamically-shaped cowl of the combustion chamber.The core flow is typically separating into three branches. One branch isthe cowl passage to supply air to fuel nozzles and for dome cooling. Theother branches are annular outer plenum and inner plenums where air isintroduced into the combustor for cooling and to complete the combustionprocess. A further portion of the air may be utilized for turbinecooling.

The pre-diffuser is exposed to large thermal gradients and requiresvarious features for anti-rotation, axial retention, and centrality withrespect to the central engine axis. These features may result in localdiscontinuities which may generate stress risers and consequentlyreduced operational life.

SUMMARY

A hot fairing structure for a pre-diffuser according to one disclosednon-limiting embodiment of the present disclosure includes aring-strut-ring structure that comprises a multiple of hollow struts anda multiple of inlets to a respective diffusion passage, one of themultiple of inlets formed between each one of the multiple of hollowstruts located between two diffusion passages.

A further aspect of the present disclosure includes that the hot fairingstructure is a full ring structure.

A further aspect of the present disclosure includes that each of themultiple of hollow struts include a cavity.

A further aspect of the present disclosure includes a passage incommunication with the cavity.

A further aspect of the present disclosure includes that the passage isin communication with a combustor section of the gas turbine engine.

A further aspect of the present disclosure includes that the inlet toeach of the multiple of diffusion passages are smaller than an exit fromthe diffusion passage.

A further aspect of the present disclosure includes that the inlet toeach of the multiple of diffusion passages are smaller than an exit fromthe diffusion passage.

A further aspect of the present disclosure includes that each of themultiple of hollow struts align with one of a respective multiple ofexit guide vanes of an exit guide vane ring.

A further aspect of the present disclosure includes that thering-strut-ring structure is cast.

A further aspect of the present disclosure includes a full ring hotfairing radial flange that extends transverse to the multiple ofdiffusion passages.

A further aspect of the present disclosure includes a firstanti-rotation feature on one side of the full ring hot fairing radialflange and a second anti-rotation feature on an opposite side of thefull ring hot fairing radial flange.

A further aspect of the present disclosure includes that the firstanti-rotation feature engages an exit guide vane ring.

A further aspect of the present disclosure includes that the secondanti-rotation feature engages a static structure.

A further aspect of the present disclosure includes that the staticstructure is subjected to a lower temperature than the ring-strut-ringstructure.

A pre-diffuser for a gas turbine engine according to one disclosednon-limiting embodiment of the present disclosure includes an exit guidevane ring having a multiple of exit guide vanes defined around an enginelongitudinal axis; and a hot fairing structure adjacent to the exitguide vane ring to form a multiple of diffusion passages defined aroundthe engine longitudinal axis, the hot fairing structure comprises aring-strut-ring structure with a multiple of hollow struts and amultiple of inlets to the respective multiple of diffusion passages, oneof the multiple of inlets formed between each of the multiple of hollowstruts.

A further aspect of the present disclosure includes that each of themultiple of hollow struts includes a cavity.

A further aspect of the present disclosure includes a passage incommunication with each cavity.

A further aspect of the present disclosure includes an outer radialinterface between a radial outer surface of the hot fairing structureand the exit guide vane ring, the outer radial interface being a fullhoop structure; and an anti-rotation feature between the hot fairingstructure and the exit guide vane ring, the anti-rotation featuresinboard of the multiple of diffusion passages.

A further aspect of the present disclosure includes a hot fairing radialflange that extends radially inward from the hot fairing structure andan exit guide vane radial flange that extends radially inward from theexit guide vane ring, the seal located between the exit guide vaneradial flange and the hot fairing radial flange.

A further aspect of the present disclosure includes a static structureflange that abuts the hot fairing radial flange; a clamp ring that abutsthe exit guide vane radial flange; and a multiple of fasteners thatfasten the clamp ring to the static structure flange.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation of the inventionwill become more apparent in light of the following description and theaccompanying drawings. It should be understood, however, the followingdescription and drawings are intended to be exemplary in nature andnon-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

Various features will become apparent to those skilled in the art fromthe following detailed description of the disclosed non-limitingembodiment. The drawings that accompany the detailed description can bebriefly described as follows:

FIG. 1 is a schematic cross-section of a gas turbine engine.

FIG. 2 is a partial longitudinal cross-sectional view of a pre-diffuseraccording to one non-limiting embodiment that may be used with the gasturbine engine shown in FIG. 1 .

FIG. 3 is an expanded cross-sectional view of the pre-diffuser.

FIG. 4 is a perspective view of the pre-diffuser.

FIG. 5 is a view from front of the pre-diffuser.

FIG. 6 is a view from rear of the pre-diffuser.

FIG. 7 is a perspective view of the hot fairing structure of thepre-diffuser.

FIG. 8 is a perspective view of the exit guide vane ring of thepre-diffuser.

FIG. 9 is a perspective view of the hot fairing structure from anopposite direction as that of FIG. 7 .

FIG. 10 is a perspective view of the static structure.

FIG. 11 is an expanded longitudinal cross-sectional view of an outerradial interface between the hot fairing structure 102 and the exitguide vane ring of the pre-diffuser.

FIG. 12 is an exploded perspective view of the hot fairing structure ofthe pre-diffuser.

FIG. 13 is an exploded cross-sectional view taken along line 13-13 inFIG. 5 .

FIG. 14 is an exploded cross-sectional view taken along line 14-14 inFIG. 13 .

FIG. 15 is an exploded cross-sectional view taken along line 14-14 inFIG. 13 of another embodiment.

DETAILED DESCRIPTION

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude other systems or features. The fan section 22 drives air along abypass flowpath while the compressor section 24 drives air along a coreflowpath for compression and communication into the combustor section26, then expansion through the turbine section 28. Although depicted asa turbofan gas turbine engine in the disclosed non-limiting embodiment,it should be understood that the concepts described herein are notlimited to use with turbofans as the teachings may be applied to othertypes of turbine engines.

The engine 20 generally includes a low spool 30 and a high spool 32mounted for rotation about an engine central longitudinal axis Arelative to an engine case structure 36 via several bearing structures38. The low spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor (LPC) 44 and a lowpressure turbine (LPT) 46. The inner shaft 40 drives the fan 42 directlyor through a geared architecture 48 to drive the fan 42 at a lower speedthan the low spool 30. An exemplary reduction transmission is anepicyclic transmission, namely a planetary or star gear system.

The high spool 32 includes an outer shaft 50 that interconnects a highpressure compressor (HPC) 52 and high pressure turbine (HPT) 54. Acombustor 56 is arranged between the HPC 52 and the HPT 54. The innershaft 40 and the outer shaft 50 are concentric and rotate about theengine central longitudinal axis A which is collinear with theirlongitudinal axes. Core airflow is compressed by the low pressurecompressor 44, then the high pressure compressor 52, mixed with the fueland burned in the combustor 56, then expanded over the HPT 54 and LPT46. The HPT 54 and LPT 46 rotationally drive the respective high spool32 and low spool 30 in response to the expansion.

With reference to FIG. 2 , the combustor 56 generally includes an outerliner 60, an inner liner 62 and a diffuser case module 64. The outerliner 60 and the inner liner 62 are spaced apart such that a combustionchamber 66 is defined therebetween. The combustion chamber 66 isgenerally annular in shape. The outer liner 60 and the inner liner 62are spaced radially inward of the outer diffuser case 64 to define anannular outer plenum 76 and an annular inner plenum 78. It should beunderstood that although a particular combustor is illustrated, othercombustor types with various combustor liner arrangements will alsobenefit herefrom. It should be further understood that the disclosedcooling flow paths are but an illustrated embodiment and should not belimited only thereto.

The liners 60, 62 contain the combustion products for direction towardthe turbine section 28. Each liner 60, 62 generally includes arespective support shell 68, 70 which supports one or more heat shields72, 74 that are attached thereto with fasteners 75.

The combustor 56 also includes a forward assembly 80 downstream of thecompressor section 24 to receive compressed airflow through apre-diffuser 100 into the combustor section 26. The pre-diffuser 100includes a hot fairing structure 102 and an exit guide vane ring 104.The exit guide vane ring 104 includes a row of Exit Guide Vanes (EGVs)108 downstream of the HPC 52. The EGVs 108 are static engine componentswhich direct core airflow from the HPC 52 between outboard and inboardwalls 110 and 112.

The pre-diffuser 100 is secured to a static structure 106 to at leastpartially form the diffuser module between the compressor section 24 andthe combustor section 26. The hot fairing structure 102 is exposed tolarge thermal gradients and directs the core airflow while forming ashell within the relatively colder static structure 106. The staticstructure 106 is thereby segregated from the core airflow and generallyoperates at a relatively lower temperature than the hot fairingstructure 102. The hot fairing structure 102 and the exit guide vanering 104 are full ring structures that are assembled in a manner thatallows common thermal growth yet still remain centered with respect tothe static structure 106 along the engine central longitudinal axis A.

With reference to FIG. 3 , the hot fairing structure 102 includes aring-strut-ring structure 118 which forms a multiple of diffusionpassages 120 that each communicate with one of a multiple of diffusionpassage ducts 124 (FIG. 4 ) that extend the diffusion passage of thering-strut-ring structure 118 along each flow passage P. Each of thediffusion passages 120 in the ring-strut-ring structure 118 includes aninlet to the pre-diffuser 100 and a diffusion passage exit that mateswith the diffusion passage duct 124. Each of the diffusion passage ducts124 include a diffusion duct inlet 126 (FIG. 5 ) adjacent to thering-strut-ring structure 118. A diffusion duct exit 128 from eachdiffusion passage duct 124 provide the outlet from the pre-diffuser 100.The diffusion duct exits 128 (FIG. 6 ) are larger than the respectivediffusion duct inlets 126 which are positioned between each of the EGVs108. In one example, the number of EGVs are 2-5 times more than thenumber of diffusion duct inlets 126. In this embodiment, the diffusionpassage ducts 124 expand primarily in the radial direction to thediffusion duct exits 128.

The hot fairing structure 102 and the exit guide vane ring 104 includean anti-rotation interface 130 that positions the anti-rotation features132, 134 in a region of low stress inboard of the diffusion passages120. In the disclosed embodiment, the hot fairing structure 102 mayinclude a multiple of circumferentially located anti-rotation tabs 132(FIG. 7 ) that engage respective anti-rotation slots 134 (FIG. 8 ) inthe exit guide vane ring 104. The inboard location of the anti-rotationfeatures 132, 134 allow the multiple, static, hot components to grow andinteract together, with low stress, and simultaneously remain alignedwith the rotating components to facilitate a longer service life andengine efficiency.

An axial extension 140 of the hot fairing structure 102 extends along aninner diameter flow surface of the flow passage P. The axial extension140 at least partially overlaps a recessed area 142 of the exit guidevane ring 104. That is, the axial extension 140 extends in a directionopposite that of the core flow in the flow passage P and overlaps therecessed area 142 (FIG. 8 ) in the exit guide vane ring 104.

A hot fairing radial flange 150 extends from the hot fairing structure102 parallel to an exit guide vane radial flange 152 of the exit guidevane ring 104. A static structure flange 154 extends radially outwardlyfrom the static structure 106 with respect to the engine axis A to abutthe hot fairing radial flange 150. That is, the static structure flange154 operates as a mount location for the hot fairing structure 102 andthe exit guide vane ring 104. The hot fairing radial flange 150 alsoincludes a multiple of circumferentially located anti-rotation tabs 156(FIG. 9 ) opposite the anti-rotation tabs 132 that engage respectiveanti-rotation slots 158 (FIG. 10 ) in the static structure flange 154 ofthe static structure 106.

A clamp ring 160 abuts the exit guide vane radial flange 152 to sandwicha seal member 170 between the exit guide vane radial flange 152 and thehot fairing radial flange 150. A seal member 170, e.g., a torsionalspring seal, dogbone, or diamond seal, that accommodates compression ofthe hot fairing structure 102 and the exit guide vane ring 104 inresponse to axial assembly of the static structure modules. A multipleof circumferentially arranged fasteners 180 fastens the clamp ring 160to the static structure 106.

An outer radial interface 190 between the hot fairing structure 102 andthe exit guide vane ring 104 includes a radial interface 192 and anaxial interface 194. Since the outer radial interface 190 of the hotfairing structure 102 and the exit guide vane ring 104 are devoid ofdiscontinuities and are uniform in cross-section around thecircumference of the full hoop structures, service life is significantlyincreased. The anti-rotation interface 130 and the outer radialinterface 190 are essentially hidden from the gas path and are locatedin low stress regions.

With reference to FIG. 12 , the ring-strut-ring structure 118 may becast from nickel alloys to provide for structural attachment andefficient sealing between turbine engine components combined withindependently manufactured thin-wall diffusion passage ducts 124. Thediffusion passage ducts 124 can be manufactured by several methodsincluding cast, sheet-metal formed, additively manufactured, orcombinations thereof. The wall thickness and local stiffness of thediffusion passage ducts 124 can be tailored to a specific requirementthereof without excessive weight as is typical of cast components. Thejoining of the diffusion passage ducts 124 to the ring-strut-ringstructure 118 to form each complete diffusion passage may be by brazing,bonding, welding, mechanical, or others. Light weight diffusion passageducts 124 reduce the overall weight of the design, simplify thering-strut-ring structure 118 casting process, and increase the naturalfrequencies of the hot fairing structure 102 by minimizing thecantilevered mass of the diffusion passage ducts 124.

With reference to FIG. 13 , the one-piece ring-strut-ring structure 118of the hot fairing structure 102 includes a multiple of hollow struts200 that align with the respective multiple of upstream EGVs 108 of theexit guide vane ring 104 and split the flow into two adjacent diffusionpassage ducts 124 (FIG. 14 ). Each of the multiple of hollow struts 200are generally airfoil shaped. In this embodiment, the hollow struts 200reduce thermal mass and thickness so that the transient thermal gradientwithin the strut is minimal. The hollow strut 200 includes a cavity 204that may be manufactured with ceramic cores, and a core exit via apassage 202 may be located at a location that has the least impact onthermal stiffness. Alternatively, the struts 200 may be solid (FIG. 15).

Each passage 202 is located along an axis D and is in communication withthe cavity 204 in the hollow strut 200. The passage 202 may bereinforced and permits diffusion air from the diffuser side of thepre-diffuser 100, i.e., the air around the combustor 56, to be receivedinto the respective cavity 204. The diffuser air facilitates thermalcontrol of the ring-strut-ring structure 118 of the hot fairingstructure 102 to reduce the mass of the ring-strut-ring structure 118.The reduced mass of the ring-strut-ring structure 118 of the hot fairingstructure 102 results in a more responsive thermal characteristic. Thestrut geometry maximizes the perimeter of the ring-strut-ring structure118 that is engaged in torsional stiffness. That is, the mass close tothe centroid 206 has little to no effect on stiffness. To resistmulti-node sinusoidal waves travelling around the circumference of thehot fairing structure 102, local torsional sectional properties of thering-strut-ring structure 118 facilitate control of the naturalfrequencies of the hot fairing structure 102.

The ring-strut-ring structure 118 with the hollow regions with the corebreakout located close to the centroid 206 of the torsional sectionforms a pre-diffuser 100 that can have both high natural frequencies andmore uniform transient thermal gradients which enables a lightweight,high performance low thermal stress design. The hot fairing structure102 with a hollow leading edge region and the core opening on the aftside of the hollow strut 200, is located about the mid-axis of theairfoil shape to connect outer diameter static structure, with minimalthermal mass, and an inner diameter static structure with distributedmass such that the transient thermal response is optimized to reducethermal stress.

The ring-strut-ring structure 118 also allows coupled Exit Guide Vaneswith the floating hot fairing to provide improved cyclic life. Lightweight tubular flowpath extensions reduce the overall weight of thedesign, simplify the ring-strut-ring structure 118 casting process, andincrease the natural frequencies of the hot fairing by minimizing thecantilevered mass of the tubes. Additionally, the torsionally stiffring-strut-ring structure 118 ensures that the design can beincorporated with features on the inner diameter structure whichfacilitates attachment to other structures with the least amount ofcontact, yet have sufficient frequency margin with respect to engineoperating vibration sources.

Although a combination of features is shown in the illustrated examples,not all of them need to be combined to realize the benefits of variousembodiments of this disclosure. In other words, a system designedaccording to an embodiment of this disclosure will not necessarilyinclude all of the features shown in any one of the figures or all ofthe portions schematically shown in the figures. Moreover, selectedfeatures of one example embodiment may be combined with selectedfeatures of other example embodiments.

It should be understood that like reference numerals identifycorresponding or similar elements throughout the several drawings. Itshould also be understood that although a particular componentarrangement is disclosed in the illustrated embodiment, otherarrangements will benefit herefrom.

The foregoing description is exemplary rather than defined by thelimitations within. Various non-limiting embodiments are disclosedherein, however, one of ordinary skill in the art would recognize thatvarious modifications and variations in light of the above teachingswill fall within the scope of the appended claims. It is therefore to beunderstood that within the scope of the appended claims, the disclosuremay be practiced other than as specifically described. For that reasonthe appended claims should be studied to determine true scope andcontent.

What is claimed:
 1. A pre-diffuser downstream of a compressor section ofa gas turbine engine, comprising: a full ring ring-strut-ring structurethat comprises a multiple of hollow struts and a multiple of inlets to amultiple of diffusion passages, one of the multiple of inlets and arespective one of the multiple of diffusion passages being between eachone of the multiple of hollow struts, wherein each of the multiple ofhollow struts comprises a cavity in communication with a combustorsection of the gas turbine engine through a passage, wherein the passagehas a passage opening on a downstream surface of each of the multiple ofhollow struts, and the passage opening is the only inlet or outlet tothe cavity for fluidic contact outside of the cavity; and a multiple ofdiffusion passage ducts extending from the ring-strut-ring structure,each of the multiple of diffusion passage ducts in communication withone of the multiple of diffusion passages.
 2. The pre-diffuser of claim1, further comprising: an exit guide vane ring adjacent to thering-strut-ring structure; an exit guide vane radial flange that extendstransversely from the exit guide vane ring; a full ring hot fairingradial flange that extends transversely from the ring-strut-ringstructure parallel to the exit guide vane radial flange of the exitguide vane ring; a first anti-rotation feature on one side of the fullring hot fairing radial flange and a second anti-rotation feature on anopposite side of the full ring hot fairing radial flange, wherein thefirst anti-rotation feature engages an exit guide vane ring and thesecond anti-rotation feature engages a static structure.
 3. Thepre-diffuser as set forth in claim 2, wherein the first anti-rotationfeature and the second anti-rotation feature are not exposed to anengine gas path of the gas turbine engine.
 4. The pre-diffuser asrecited in claim 1, wherein the inlet to each of the multiple ofdiffusion passages are smaller than an exit from the diffusion passage.5. The pre-diffuser as recited in claim 1, wherein each of the multipleof hollow struts align with one of a respective multiple of exit guidevanes of an exit guide vane ring.
 6. A pre-diffuser for a gas turbineengine, comprising: an exit guide vane ring having a multiple of exitguide vanes defined around an engine longitudinal axis; and a hotfairing structure adjacent to the exit guide vane ring to form amultiple of diffusion passages defined around the engine longitudinalaxis, the hot fairing structure comprises a ring-strut-ring structurewith a multiple of hollow struts and a multiple of inlets to a multipleof diffusion passages, one of the multiple of inlets and a respectiveone of the multiple of diffusion passages being between each one of themultiple of hollow struts, wherein each of the multiple of hollow strutscomprises a cavity in communication with a combustor section of the gasturbine engine through a passage, wherein the passage is closed facingupstream and has a passage opening on a downstream surface of each ofthe multiple of hollow struts such that air from the combustor sectionof the gas turbine engine enters the cavity to provide thermal controlof the ring-strut-ring structure, wherein the passage opening is theonly inlet or outlet to the cavity for fluidic contact outside of thecavity.
 7. The pre-diffuser as set forth in claim 6, further comprising:a multiple of diffusion passage ducts extending from the ring-strut-ringstructure, each of the multiple of diffusion passage ducts incommunication with one of the multiple of diffusion passages.
 8. Thepre-diffuser as recited in claim 6, further comprising: an outer radialinterface between a radial outer surface of the hot fairing structureand the exit guide vane ring, the outer radial interface being a fullhoop structure; and an anti-rotation feature between the hot fairingstructure and the exit guide vane ring, the anti-rotation featuresinboard of the multiple of diffusion passages.
 9. The pre-diffuser asrecited in claim 8, wherein the outer radial interface and theanti-rotation feature are not exposed to an engine gas path of the gasturbine engine.
 10. The pre-diffuser as recited in claim 6, furthercomprising: a hot fairing radial flange that extends radially inwardfrom the hot fairing structure; and an exit guide vane radial flangethat extends radially inward from the exit guide vane ring, the seallocated between the exit guide vane radial flange and the hot fairingradial flange.
 11. The pre-diffuser as recited in claim 6, furthercomprising: a static structure flange that abuts the hot fairing radialflange; a clamp ring that abuts the exit guide vane radial flange; and amultiple of fasteners that fasten the clamp ring to the static structureflange.